310/​320Skyknight

Parts most often named Nut (27) · Retain Bearing (25) · Dowel (21) · Cylinder Pin (19)

PART HAD APPROX 700.00 HOURS SINCE OVERHAUL, FATIGUE CRACK APPEARS TO HAVE ORIGINATED AT FORWARD BOLT HOLE. PROPELLER/ENGINE BEGAN VIBRATING IN FLIGHT DUE TO COUNTER WEIGHT SHIFTING ON FERRULE. AIRCRAFT REDUCED POWER, LANDED AND WAS REPAIRED BEFORE FURTHER FLIGHT. (K)

(AUS) PROPELLER FAULTY. FOLLOWING FEATHERING CHECK IAW AD/PROP/2 AMDT2IT WAS FOUND THAT TWO BLADES COULD BE ROTATED BACK TO FULL FINE POSITION BY HAND.

(CAN) PROPELLER RECEIVED FOR AD 97-18-02 REPETITIVE INSPECTION. CRACK DISCOVERED DURING M.P.I. INSPECTION OF THE CLAMPS. AT ONE TIME DURING THE HISTORY OF THE PROP THE COUNTERWEIGHT SHOWS DAMAGE FROM CONTACT AGAINST THE PROP PISTON. PUSHING OUT THE THIN WALL AND LEAVING A CRACK 1/2 INCH LONG.

Parts most often named Bellcrank (35) · Torque Tube (23) · Rod End (9) · Tube (8)

AFTER INCIDENT ON 12/21/2021 AT KBCT. PER REQUEST AIRCRAFT WAS JACKED AND FUNCTIONAL CHECKS (GEAR SWINGS) WERE PERFORMED ON THE AIRCRAFT. AFTER MULTIPLE FUNCTIONAL CHECKS (GEAR SWINGS) IT WAS FOUND THAT THE NOSE GEAR WOULD NOT LOCK OUT AND A GRINDING NOISE WAS HEARD COMING FROM THE LANDING GEAR ACTUATOR ASSEMBLY (PN: 0894000-4, [S/N removed]).

BELLCRANK FORK ASSEMBLY BROKE WHILE EXTENDING THE LANDING GEAR FOR LANDING CAUSING THE NOSE GEAR TO NOT EXTEND. AIRCRAFT LANDED WITH MAIN GEAR ONLY.

RIGHT MAIN LANDING GEAR COLLAPSED AFTER LANDING. PILOT MADE A LEFT TURN CAUSING RIGHT GEAR TO COLLAPSE. INSPECTION FOUND THE TORQUE TUBE BRACKET ASSEMBLY BROKEN AT THE PIVOT BEARING, CAUSING THE DOWN LOCK TENSION TO BE NONEXISTENT. FAILURE OF THE TORQUE RUBE ASSEMBLY DID NOT APPLY SUFFICIENT DOWN LOCK TENSION.

Parts most often named Hub (78) · Spider (1) · Stud (1) · Propeller (1)

PROPELLER SENT TO OUR REPAIR STATION FOR RED DYE LEAK CHECK. PROPELLER WAS DISASSEMBLED AND INSPECTED NR 1 AND NR 3 BLADE FERRULE WERE DRILLED TOO DEEP. NR 2 BLADE SOCKET WAS FILLED WITH RTV. NR 2 BLADE BEARING AND BALLS AND FERRULE WERE CONDEMNED FOR RUST FROM RTV. PROPELLER HUB WAS CRACKED. UN-AIRWORTHY PARTS RETURNED TO CUSTOMER.

(CAN) NUMBER 1 BLADE WAS LEAKING OIL FROM THE HUB. PROP WAS REMOVED AND SENT TO O/H SHOP. SEAL IN HUB WAS FOUND TO BE LEAKING. SEAL REPLACED -PROP WAS REINSTALLED.

PART CRACKED FROM GREASE FITTING HOLE ACROSS BACK OF HUB TO OPPOSITE SIDE. SENT TO HARTZEL PROPELLER FOR EVALUATION. (X)

Parts most often named Blade (77) · Actuating Pin (2) · Ferrule (2) · Blade Act Pin (2)

DURING INSPECTION FOR AD 97-18-02, BOTH PROPELLER BLADES WERE FOUND CRACKED USING PHASE ANALYSIS EDDY CURRENT INSPECTION TECHNIQUE. BOTH BLADES CONTAIN SEVERAL SMALL CRACKS NOT DETECTABLE USING AN ED520 OR SIMILAR METER BASED INSTRUMENTS. SUBMITTER RECOMMENDED PERSONNEL PERFORMING INSPECTIONS CONSIDER UPGRADING TO PHASE SENSITIVE INSTRUMENTATION.

(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER BLADES WERE FOUND STONE DAMAGED. THE PROPELLER BLADES WERE TRIMMED.

(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND ON THE PROPELLER BLADES. THE BLADES WERE TRIMMED.

Parts most often named Cylinder (14) · Cylinder Head (6) · Lifter (4) · Exhaust Valve (4)

AFTER TAKE OFF AND IN CLIMB OUT, THE TOWER REPORTED SMOKE TRAILING THE LEFT ENGINE. RETURNED TO DEPARTURE WITHOUT INCIDENT. REMOVED COWL AND FOUND OIL DRIPPING FROM THE NR 3 CYLINDER. FOUND THE GASKET ON THE NR 3 CYLINDER HAD COLLAPSED IN UPPER RIGHT CORNER. REPLACED THE VALVE COVER GASKET AND CLEANED OIL RESIDUE. RAN ENGINE FOR LEAK AND OPERATIONAL CHECKS, NO LEAKS AND PERFORMANCE NORMAL.

(CAN) OWNER REPORTED A SMALL OIL LEAK ON BOTH ENGINES. UPON INVESTIGATING IT WAS FOUND THAT EACH ENGINE HAD A CRACKED CYLINDER HEAD. 4 CYLINDERS WERE REPLACED 90 HOURS PRIOR WITH THE SAME PROBLEM. LT CYLINDER NR 6 CRACKED ON INTAKE PORT WHERE YOU COULD SEE BLUE STREAKING IN BETWEEN FINS. RT CYLINDER NR 1 CRACKED IN THE SAME MANNER.

WHILE ON A 3 MILE FINAL, OIL STARTED APPEARING ON THE RIGHT ENGINE NACELLE AND THE PILOT REPORTED A VIBRATION. AFTER AN UN EVENTFUL LANDING, THE ACFT TAXIED BACK UNDER ITS OWN POWER. THE MECHANIC FOUND THAT THE RT ENGINE NR 2 CYLINDER HEAD WAS STARTING TO SEPARATE FROM THE CYLINDER BARREL BY ABOUT .5".

Parts most often named Lifter (7) · Crankcase (5) · Crankshaft (3) · Connecting Rod (2)

NR 1 AND NR 2 TOP RING LAN FAILURE. ENGINE LOSS OF COMRESSION. FOUND LOOKING AT TOP OF PISTON FROM ABOUT 7 O`CLOCK POSITION TO 11 O`CLOCK RING LAN MISSING AND BROKEN RINGS. OPERATION AT 11,000 FT, 68 PERCENT POWER ENGINE DEVELOPED A VIBRATION. POSSIBLE DEFECTIVE PISTON.

(CAN) ENGINE WAS REMOVED FOR REPAIR AFTER FINDING METAL IN THE FILTER. IT WAS DISCOVERED THAT THE 6 INTAKE LIFTERS WERE FAILED OR FAILING. THESE LIFTERS WERE PART OF A NEW CAMSHAFT AND LIFTER KIT. THESE LIFTERS WERE MFG JUST BEFORE MANDATORY SB 09-8A. AWD. 2010-11-04. BELIEVE THAT THESE LIFTERS SHOULD HAVE BEEN RECALLED AS WELL.

WHEN REMOVING RT ENGINE NR 4 CYLINDER DUE TO A CRACK, NR 4 PISTON SKIRT FOUND BROKE OFF AT THE 4TH RING LAND. ENGINE THEN REMOVED FROM ACFT FOR TEAR-DOWN INSPECTION. I HAVE FOUND BROKEN PISTON SKIRTS ON THIS PARTICULAR ACFT ON 3 DIFFERENT ENGINES.

Parts most often named Switch (17) · Microswitch (2) · Downlock Switch (2) · Actuator (1)

DURING LANDING, THE PILOT COULD NOT VERIFY THAT THE NOSE LANDING GEAR WAS DOWN AND LOCKED DUE TO NO INDICATION IN THE COCKPIT. ON INSPECTION, THE NOSE LANDING GEAR INDICATOR ASSEMBLY LAMP SOCKET WAS FOUND TO BE FAULTY.

(CAN) UPON APPROACH THE LANDING GEAR WAS SELECTED DOWN WITH NO GREEN LIGHT DOWN AND LOCKED INDICATION ON THE RT GEAR. THE GEAR WAS CYCLED, THE MANUAL EXTENSION WAS PERFORMED ALL WITH THE SAME RESULT. THE AIRCRAFT LANDED UNEVENTFULLY AND UPON INVESTIGATION THE MICRO SWITCH ACTUATOR TAB WAS FOUND BROKEN AT THE ATTACHING BRACKET. THE ACUATOR WAS REPLACED AND THE GEAR WAS SWUNG NUMEROUS TIMES [S/N removed].

ON APPROACH TO ELP THE PILOT DID NOT HAVE A GREEN LIGHT AFTER SELECTING GEAR DOWN. A FLY BY INDICATED GEAR APPEARED IN NORMAL DOWN POSITION. PILOT LANDED WITHOUT INCIDENT. THE LEFT HAND MICRO SWITCH PN 1SE3-3 FAILED INTERNALLY. REMOVED AND REPLACED SWITCH.

Parts most often named Pump (20) · Switch (1)

ON THE LEFT SIDE OF AC, WE HAVE REPLACED THE CIRCULATING PUMP NUMEROUS TIMES WHILE RIGHT SIDE HAS BEEN FINE. MOST RECENT DATES OF REPLACEMENT AS FOLLOWS: 12-9-99 TACH 3443.5, 9-18-2000 3715.3, 12-29-2000 3882.4. AS STATED EARLIER ALL 3 OF THESE WERE ON THE LEFT SIDE. ON 12-29-2000, WE INSPECTED THE WIRING AND BOTH INLET AND OUTLET HOSES/LINES FOR OBSTRUCTIONS. EACH PUMP WHEN REMOVED WAS VERY INTERMITTEN AND WOULD WORK WHEN THE CASING WAS TAPPED ON. PUMP NEEDS IMPROVEMENT.

(AUS) LEFT FUEL TRANSFER PUMP FAILED. INVESTIGATION FOUND THAT THE PUMP POSITIVE WIRE HAD BURNED OFF AT THE HOUSING. LEFT LANDING LIGHT CIRCUIT BREAKER TRIPPED. (X)

(AUS) RIGHT FUEL TRANSFER PUMP FAILED. INVESTIGATION FOUND THAT THE PUMP POSITIVE WIRE HAD BURNED OFF AT THE HOUSING. RIGHT LANDING LIGHT CIRCUIT BREAKER TRIPPED.

Parts most often named Bellcrank (15) · Rod End (3) · Link (1) · Arm (1)

POST FLIGHT INSPECTION DISCOVERED RIGHT INBOARD MAIN LANDING GEAR DOOR IN THE OPEN POSITION. FOUND CRACKED BELLCRANK. NO ADVERSE EFFECTS NOTICED DURING THE PREVIOUS FLIGHT. NO ADDITIONAL NOISE OR VIBRATION. NO OBVIOUS CAUSE NOTED FOR FAILURE.REPLACED BELLCRANK OPERATION NORMAL.

PILOT REPORTED ENCOUNTERING SEVERE TURBULENCE UPON APPROACH TO LANDING. UPON RETURN TO BASE, PILOT NOTICED THAT RT INNER GEAR DOOR WAS HANGING OPEN. UPON FURTHER INSPECTION, FOUND BELLCRANK BROKEN, PN 08411066.

ROD END FAILED, ALLOWING NOSE GEAR DOOR TO PARTIALLY CLOSE IN FLIGHT. WHEN GEAR WAS RETRACTED, JAMMED NOSE GEAR ASSY ALONG WITH GEAR DOOR UP IN GEAR WELL. (K)

Parts most often named Spacer (2) · Washer (2) · Pin (1) · Idler Assy (1)

DURING THE LANDING PORTION OF OUR FLIGHT ON THE ROLL OUT THE RIGHT GEAR COLLAPSE UNDERNEATH THE AIRPLANE. UPON FURTHER INSPECTION IT WAS DETERMINED THAT THE BOLT HOLDING THE FOLLOWING SIDE BRACE AND DOWN LOCK SHEARD CAUSING THE RIGHT SIDE BRACE LOCK LINK ASSEMBLY P/N 084100-4 TO FAIL.

AFTER LANDING, LT MLG STRUT WAS DISCOVERED TO BE FLAT. INITIAL INSPECTION REVEALED THAT THE SCHRADER VALVE HAD FAILED, BUT AFTER VALVE REPLACEMENT, THE STRUT WOULD STILL NOT REMAIN INFLATED. FURTHER INSPECTION REVEALED THAT THE STRUT WAS ALSO LEAKING FROM THE UPPER STRUT SEAL. THE STRUT WAS REMOVED AND DISASSEMBLED, REVEALING CORROSION IN THE UPPER TRUSS ASSEMBLY BARREL. REBUILT STRUT USING CERTIFIED UPPER TRUSS ASSEMBLY AND NEW SEALS.

WASHER WAS NOT INSTALLED UNDER THE HEAD OF CENTER TORQUE LINK FOR THE RT MLG. THE MISSING WASHER ALLOWED THE CENTER TORQUE LINK BOLT TO PULL THE TORQUE LINK BUSHING, PN 0841000-99 THROUGH THE TORQUE LINK, PN 0841000-64 ALLOWING THE TORQUE LINKS TO SEPARATE AND THE MLG STRUT AND WHEEL ASSY TO ROTATE 90 DEGREES.